In-Space LOX/Methane Pintle Propulsion Engine (LMPPE) Evaluation and Demonstration

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX15CM59P
Agency Tracking Number: 155137
Amount: $124,823.00
Phase: Phase I
Program: SBIR
Awards Year: 2015
Solicitation Year: 2015
Solicitation Topic Code: H2.01
Solicitation Number: N/A
Small Business Information
238 Business Park Boulevard, Building 23B Suite J, Madison, AL, 35758-7553
DUNS: 127963515
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Pete Markopoulos
 Senior Engineering Specialist
 (256) 461-8522
 pete.markopoulos@kte-aerospace.com
Business Contact
 Richard Webb
Title: Business Official
Phone: (256) 461-8522
Email: richard.webb@kte-aerospace.com
Research Institution
N/A
Abstract
KTE's proposed innovation is the LOx/Methane Pintle Propulsion Engine or (LMPPE), which can offer higher reliability, lower cost and higher performance than conventional impinging injector-based combustion devices for in space propulsion systems. The concept can be used in both pump and pressure-fed engine architectures. The LMPPE builds upon the Catalytically Initiated Combustor (CIC) igniter technology previously demonstrated to a high TRL coupled with a low cost pintle main injector that has potential to provide a path for a LOx/Methane upper stage engine that is dynamically stable offering high performance with a wide throttle capability over a range of propellant inlet conditions. The CIC based pintle propulsion engine also offers attractive packaging advantages and improved reliability and operability while reducing development costs and risks for upper-stage engines. The pintle propulsion approach requires looser tolerances of the components and can be successfully fabricated from a number of additive manufacturing approaches. This multi-functional capability will further reduce cost and improve reliability in launch or in-space vehicles by increasing component production rates and reducing part count. The focus of the proposed effort is to prove the feasibility of this novel oxygen/methane pintle engine. The in-space engine can be designed to operate at lower chamber pressures, lending itself to the use of composite and additive manufactured components. The design offers an inherent combustion stability allowing simpler combustion chamber designs and ease of fabrication due to the omission of complex acoustic damping devices. Therefore, an expensive development programs can be avoided due to the very low risk of combustion instability.

* Information listed above is at the time of submission. *

Agency Micro-sites

SBA logo
Department of Agriculture logo
Department of Commerce logo
Department of Defense logo
Department of Education logo
Department of Energy logo
Department of Health and Human Services logo
Department of Homeland Security logo
Department of Transportation logo
Environmental Protection Agency logo
National Aeronautics and Space Administration logo
National Science Foundation logo
US Flag An Official Website of the United States Government